EP2348193A3 - Composite fan blade with a recamberable leading edge and method of manufacture - Google Patents

Composite fan blade with a recamberable leading edge and method of manufacture Download PDF

Info

Publication number
EP2348193A3
EP2348193A3 EP11250079.8A EP11250079A EP2348193A3 EP 2348193 A3 EP2348193 A3 EP 2348193A3 EP 11250079 A EP11250079 A EP 11250079A EP 2348193 A3 EP2348193 A3 EP 2348193A3
Authority
EP
European Patent Office
Prior art keywords
recamberable
manufacture
leading edge
fan blade
composite fan
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP11250079.8A
Other languages
German (de)
French (fr)
Other versions
EP2348193A2 (en
Inventor
Phillip Alexander
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2348193A2 publication Critical patent/EP2348193A2/en
Publication of EP2348193A3 publication Critical patent/EP2348193A3/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A method of forming a vibration stable airfoil by forming a composite blade having a metallic sheath (17) thereon. The sheath has a head section (19) extending out from the blade by a sufficient distance to permit deformation of the head section. The airfoil (20) is tested to determine the vibrational stability thereof; and the head section is re-cambered to adjust the vibrational stability to a desired level.
EP11250079.8A 2010-01-26 2011-01-26 Composite fan blade with a recamberable leading edge and method of manufacture Withdrawn EP2348193A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/693,754 US20110182741A1 (en) 2010-01-26 2010-01-26 Composite fan blade leading edge recamber

Publications (2)

Publication Number Publication Date
EP2348193A2 EP2348193A2 (en) 2011-07-27
EP2348193A3 true EP2348193A3 (en) 2013-06-19

Family

ID=43629584

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11250079.8A Withdrawn EP2348193A3 (en) 2010-01-26 2011-01-26 Composite fan blade with a recamberable leading edge and method of manufacture

Country Status (2)

Country Link
US (1) US20110182741A1 (en)
EP (1) EP2348193A3 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8075274B2 (en) * 2009-05-13 2011-12-13 Hamilton Sundstrand Corporation Reinforced composite fan blade
GB201309280D0 (en) * 2013-05-23 2013-07-10 Rolls Royce Plc Aerofoil Recambering
JP2016527426A (en) 2013-05-29 2016-09-08 ゼネラル・エレクトリック・カンパニイ Composite airfoil metal patch
CA2936196A1 (en) 2014-01-16 2015-07-23 General Electric Company Composite blade root stress reducing shim
US9879539B2 (en) 2014-11-18 2018-01-30 Honeywell International Inc. Engine airfoils and methods for reducing airfoil flutter
US9745851B2 (en) 2015-01-15 2017-08-29 General Electric Company Metal leading edge on composite blade airfoil and shank
US11149642B2 (en) 2015-12-30 2021-10-19 General Electric Company System and method of reducing post-shutdown engine temperatures
US11053861B2 (en) 2016-03-03 2021-07-06 General Electric Company Overspeed protection system and method
US10677259B2 (en) 2016-05-06 2020-06-09 General Electric Company Apparatus and system for composite fan blade with fused metal lead edge
US10337405B2 (en) 2016-05-17 2019-07-02 General Electric Company Method and system for bowed rotor start mitigation using rotor cooling
US10138732B2 (en) 2016-06-27 2018-11-27 United Technologies Corporation Blade shield removal and replacement
US10583933B2 (en) 2016-10-03 2020-03-10 General Electric Company Method and apparatus for undercowl flow diversion cooling
US10947993B2 (en) 2017-11-27 2021-03-16 General Electric Company Thermal gradient attenuation structure to mitigate rotor bow in turbine engine
US11879411B2 (en) 2022-04-07 2024-01-23 General Electric Company System and method for mitigating bowed rotor in a gas turbine engine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3368795A (en) * 1967-07-12 1968-02-13 Gen Motors Corp Composite rotor blade having high modal frequencies
US4118147A (en) * 1976-12-22 1978-10-03 General Electric Company Composite reinforcement of metallic airfoils
EP0496550A1 (en) * 1991-01-25 1992-07-29 General Electric Company Wide chord fan blade
US5785498A (en) * 1994-09-30 1998-07-28 General Electric Company Composite fan blade trailing edge reinforcement
US5887332A (en) * 1996-02-29 1999-03-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Hybrid component with high strength/mass ratio and method of manufacturing said component
US6893211B1 (en) * 1999-11-24 2005-05-17 Miu Aero Engines Gmbh Lightweight structural component having a sandwich structure
US20050278950A1 (en) * 2004-03-08 2005-12-22 Snecma Moteurs Process for manufacturing a reinforcing leading or trailing edge for a fan blade
US20060263222A1 (en) * 2005-05-18 2006-11-23 Vetters Daniel K Composite filled gas turbine engine blade with gas film damper

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE755608A (en) * 1969-09-04 1971-02-15 Gen Electric COMPRESSOR BLADES
US4022547A (en) * 1975-10-02 1977-05-10 General Electric Company Composite blade employing biased layup
USRE34207E (en) * 1986-11-19 1993-03-30 General Electric Company Counterrotating aircraft propulsor blades
US5102300A (en) * 1988-10-07 1992-04-07 United Technologies Corporation Pinned airfoil propeller assembly
US5269658A (en) * 1990-12-24 1993-12-14 United Technologies Corporation Composite blade with partial length spar
FR2684719B1 (en) * 1991-12-04 1994-02-11 Snecma BLADE OF TURBOMACHINE COMPRISING PLASTS OF COMPOSITE MATERIAL.
US5279892A (en) * 1992-06-26 1994-01-18 General Electric Company Composite airfoil with woven insert
US5509781A (en) * 1994-02-09 1996-04-23 United Technologies Corporation Compressor blade containment with composite stator vanes
US5520532A (en) * 1994-08-01 1996-05-28 United Technologies Corporation Molding assembly for forming airfoil structures
US5908285A (en) 1995-03-10 1999-06-01 United Technologies Corporation Electroformed sheath
US5939006A (en) * 1995-06-28 1999-08-17 General Electric Company Method for forming a composite airfoil structure
JPH1054204A (en) * 1996-05-20 1998-02-24 General Electric Co <Ge> Multi-component blade for gas turbine
US5881972A (en) * 1997-03-05 1999-03-16 United Technologies Corporation Electroformed sheath and airfoiled component construction
US6413051B1 (en) * 2000-10-30 2002-07-02 General Electric Company Article including a composite laminated end portion with a discrete end barrier and method for making and repairing
US6607358B2 (en) * 2002-01-08 2003-08-19 General Electric Company Multi-component hybrid turbine blade
FR2861143B1 (en) * 2003-10-20 2006-01-20 Snecma Moteurs TURBOMACHINE BLADE, IN PARTICULAR BLADE OF BLOWER AND METHOD OF MANUFACTURING THE SAME
US7186092B2 (en) * 2004-07-26 2007-03-06 General Electric Company Airfoil having improved impact and erosion resistance and method for preparing same
US7655581B2 (en) * 2005-11-17 2010-02-02 Albany Engineered Composites, Inc. Hybrid three-dimensional woven/laminated struts for composite structural applications
GB0610372D0 (en) * 2006-05-25 2006-07-05 Smiths Group Plc Blades

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3368795A (en) * 1967-07-12 1968-02-13 Gen Motors Corp Composite rotor blade having high modal frequencies
US4118147A (en) * 1976-12-22 1978-10-03 General Electric Company Composite reinforcement of metallic airfoils
EP0496550A1 (en) * 1991-01-25 1992-07-29 General Electric Company Wide chord fan blade
US5785498A (en) * 1994-09-30 1998-07-28 General Electric Company Composite fan blade trailing edge reinforcement
US5887332A (en) * 1996-02-29 1999-03-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Hybrid component with high strength/mass ratio and method of manufacturing said component
US6893211B1 (en) * 1999-11-24 2005-05-17 Miu Aero Engines Gmbh Lightweight structural component having a sandwich structure
US20050278950A1 (en) * 2004-03-08 2005-12-22 Snecma Moteurs Process for manufacturing a reinforcing leading or trailing edge for a fan blade
US20060263222A1 (en) * 2005-05-18 2006-11-23 Vetters Daniel K Composite filled gas turbine engine blade with gas film damper

Also Published As

Publication number Publication date
US20110182741A1 (en) 2011-07-28
EP2348193A2 (en) 2011-07-27

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